Hello, may I ask a question? If I set the angle of attack to 16 degrees, will(downward) cl and cd increase? Thank you, I would appreciate it if you could respond.
What happened to the "solid" cell zone condition? The solid was used to project lines to create leading and trailing edges. In the meshing stage it was hidden, but never deactivated or removed. Thanks
HI can you please make the second part again it was little bit blur at the beginning and could not see properly what operation you have done and the numerical values which you have given.
May you help me illustrating why I had got "reversed flow" in my iterations? And I have set my walls' BCs as stationary walls but "specified shear" not "No Slip" and I didn't observe that you changed any of the walls conditions, So could you explain that? I did that because the walls are free slip walls. Thanks a lot!
Hello, thanks for your tutorial. It's very easy to follow. i'm a new Fluent user. I'm trying to repeat your tutorial step by step with another NACA airfoil. The geometry and the meshing were fine but when i checked the mesh quality in fluent console, i have had negative volume problem and left-handed faced. Do you have any suggestion?
Thank you for your support. First you need to fix the left-handed faces and then negative volume by following this: www.eureka.im/4581.html Or try to change max thickness of inflation layer, or sizing at the airfoil.
How much time taken to run this??? For results....it has taken too much time is this supportive in 4gb ram would it take much time to show output results we need
In my case the mesh quality was bizzare as the minimum orthogonal mesh quality 0.01. It should be at least 0.15 to get accurate results. Anyone who can correct me what wrong was I doing?
The velocity on surfaces of the wing is near to zero, so there must be blue at all. You can see velocity vectors by making a cross-sectional shape perpendicular to the wing.
Hello very nice tutorial!Could you please ,explain the logic for setting in Cd monitor X direction cos(alfa) ,Y sin(alfa) and for Cl Monitor X: -sin(alfa); Y:cos(alfa)?Thanks a lot!
It's just the transformation from wind system to body system. if alfa>0 then the projections of Lift and Drag on the axis of body system must be (-sin(alfa),cos(alfa)) and (cos(alfa),sin(alfa)).
Hello, may I ask a question? If I set the angle of attack to 16 degrees, will(downward) cl and cd increase? Thank you, I would appreciate it if you could respond.
What happened to the "solid" cell zone condition? The solid was used to project lines to create leading and trailing edges. In the meshing stage it was hidden, but never deactivated or removed. Thanks
Sir, changing the angle of attack means changing the force monitors with cos and sine angles or any other changes are required during setup????
HI can you please make the second part again it was little bit blur at the beginning and could not see properly what operation you have done and the numerical values which you have given.
May you help me illustrating why I had got "reversed flow" in my iterations?
And I have set my walls' BCs as stationary walls but "specified shear" not "No Slip" and I didn't observe that you changed any of the walls conditions, So could you explain that? I did that because the walls are free slip walls.
Thanks a lot!
Hello, thanks for your tutorial. It's very easy to follow. i'm a new Fluent user. I'm trying to repeat your tutorial step by step with another NACA airfoil. The geometry and the meshing were fine but when i checked the mesh quality in fluent console, i have had negative volume problem and left-handed faced. Do you have any suggestion?
Thank you for your support.
First you need to fix the left-handed faces and then negative volume by following this:
www.eureka.im/4581.html
Or try to change max thickness of inflation layer, or sizing at the airfoil.
Why you choose turbulent model i got laminar flow for that dimension pls give reply
that cl and cd angle of attack parameters same for -2 deg , otherwise i need to change the sign conversion
How much time taken to run this??? For results....it has taken too much time is this supportive in 4gb ram would it take much time to show output results we need
How can I make a 30deg sweptback wing with a taper ratio of 0.7?
In my case the mesh quality was bizzare as the minimum orthogonal mesh quality 0.01. It should be at least 0.15 to get accurate results.
Anyone who can correct me what wrong was I doing?
why u skip mesh?
Sir, is that 100m/s velocity of wing or air??
what is the difference ? it's the velocity of one relative to another.
is there way to see velocity magnitude on the wing i tried but it shows me only blue
The velocity on surfaces of the wing is near to zero, so there must be blue at all. You can see velocity vectors by making a cross-sectional shape perpendicular to the wing.
Turn on to mach number, on multiple cross sections of wing
ATTACK ANGLE, WHERE DEFINED
Hello very nice tutorial!Could you please ,explain the logic for setting in Cd monitor X direction cos(alfa) ,Y sin(alfa) and for Cl Monitor X: -sin(alfa); Y:cos(alfa)?Thanks a lot!
It's just the transformation from wind system to body system. if alfa>0 then the projections of Lift and Drag on the axis of body system must be (-sin(alfa),cos(alfa)) and (cos(alfa),sin(alfa)).
hello!! how to angle of attack as we need?
X-Componet of Flow Direction = cos (angle of attack) and Y-Component of Flow Direction = sen (angle of attack)
How to see the final CD and cl values????
You can see it's values at 7:48 or use "report" to print out these coefficients.
HTC thank u